Retractable exhaust liner segment for gas turbine engines

Abstract

A retractable exhaust liner segment according to an exemplary aspect of the present disclosure includes, among other things, a first retractable exhaust liner segment which defines a first flange and a second retractable exhaust liner segment which defines a second flange. A fastener assembly received by the first flange and the second flange is configured to mount the first retractable exhaust liner segment and the second retractable exhaust liner segment. A forward end of the retractable exhaust liner segment overlaps an aft end of an engine structure and an aft end of the retractable exhaust liner segment overlaps a forward end of an exhaust liner in an assembled position. A gap exists between the retractable exhaust liner segment and one of the engine structure and the exhaust liner as the retractable exhaust liner segment is moved along an axis in one direction to a disassembled position and the gap closes as the retractable exhaust liner segment is moved along the axis in other direction to the assembled position. A method of maintaining a gas turbine engine is also disclosed.

What is claimed is: 
     
       1. A retractable exhaust liner segment comprising:
 a first retractable exhaust liner segment which defines a first flange; 
 a second retractable exhaust liner segment which defines a second flange; 
 a fastener assembly received by said first flange and said second flange configured to mount said first retractable exhaust liner segment and said second retractable exhaust liner segment; 
 wherein a forward end of said retractable exhaust liner segment overlaps an aft end of an engine structure and an aft end of said retractable exhaust liner segment overlaps a forward end of an exhaust liner in an assembled position; and 
 wherein a gap exists between said retractable exhaust liner segment and one of the engine structure and the exhaust liner as said retractable exhaust liner segment is moved along an axis in one direction to a disassembled position and the gap closes as said retractable exhaust liner segment is moved along the axis in other direction to the assembled position. 
 
     
     
       2. The retractable exhaust liner segment as recited in  claim 1 , wherein said first retractable exhaust liner segment and said second retractable exhaust liner segment are each approximately 180 degrees in circumference. 
     
     
       3. The retractable exhaust liner segment as recited in  claim 1 , wherein said fastener assembly includes a T-bolt. 
     
     
       4. The retractable exhaust liner segment as recited in  claim 3 , further comprising a retainer to retain said T-bolt within said first flange. 
     
     
       5. The retractable exhaust liner segment as recited in  claim 4 , wherein said second flange includes a slot to receive said T-bolt. 
     
     
       6. A propulsion system comprising:
 a gas turbine engine along an axis; 
 an exhaust liner along the axis; 
 a retractable exhaust liner segment between said gas turbine engine and said exhaust liner; 
 wherein a forward end of the retractable exhaust liner segment overlaps an aft end of an engine structure and an aft end of said retractable exhaust liner segment overlaps a forward end of the exhaust liner in an assembled position; and 
 wherein a gap exists between said retractable exhaust liner segment and one of the engine structure and the exhaust liner as said retractable exhaust liner segment is moved along the axis in one direction to a disassembled position and the gap closes as said retractable exhaust liner segment is moved along the axis in other direction to the assembled position. 
 
     
     
       7. The system as recited in  claim 6 , wherein said retractable exhaust liner segment includes a first segment and a second segment each approximately 180 degrees in circumference. 
     
     
       8. The system as recited in  claim 7 , wherein said first segment defines a first flange and said second segment defines a second flange. 
     
     
       9. The system as recited in  claim 8 , further comprising a fastener assembly received by said first flange and said second flange to mount said first retractable exhaust liner segment and said second retractable exhaust liner segment. 
     
     
       10. The system as recited in  claim 9 , further comprising a retainer to retain a T-bolt within said first flange. 
     
     
       11. The retractable exhaust liner segment as recited in  claim 10 , wherein said second flange includes a slot to receive said T-bolt. 
     
     
       12. The retractable exhaust liner segment as recited in  claim 6 , wherein said retractable exhaust liner segment and said exhaust liner are mounted within an outer exhaust duct, said outer exhaust duct mountable to said gas turbine engine through an exhaust duct segment. 
     
     
       13. The system as recited in  claim 12 , wherein said gas turbine engine is movable relative to said exhaust liner in a direction transverse to said axis when said retractable exhaust liner segment located in an open position such that said retractable exhaust liner segment is telescoped over one of said portion of said gas turbine engine and said exhaust liner, and said retractable exhaust liner segment is configured to oppose relative movement between said portion of said gas turbine engine and said exhaust liner when said retractable exhaust liner segment is located in a closed position. 
     
     
       14. The system as recited in  claim 12 , wherein said portion of said gas turbine engine is an engine tail cone configured to direct engine core flow to said exhaust liner. 
     
     
       15. The system as recited in  claim 14 , wherein said exhaust liner and said gas turbine engine are selectively received in an airframe configured to oppose axial movement of said exhaust liner and said gas turbine engine along the axis in a direction away from said retractable exhaust liner segment. 
     
     
       16. The system as recited in  claim 12 , wherein said gas turbine engine includes a compressor section, a combustor section and a turbine section. 
     
     
       17. A method of maintaining a gas turbine engine comprising:
 telescoping a retractable exhaust liner segment along an axis over one of a gas turbine engine and an exhaust liner such that said retractable exhaust liner segment defines a clearance gap between the other one of said gas turbine engine and said exhaust liner; and 
 moving one of said gas turbine engine or said exhaust liner transverse to the axis and through said clearance gap. 
 
     
     
       18. The method as recited in  claim 17 , wherein the exhaust liner is selectively received within an outer exhaust duct. 
     
     
       19. The method as recited in  claim 17 , wherein moving the retractable exhaust liner segment further comprises pivoting a T-bolt relative to the retractable exhaust liner segment. 
     
     
       20. The method as recited in  claim 17 , wherein moving one of the gas turbine engine or the exhaust liner transverse to the axis is performed vertically with respect to an airframe configured to receive the gas turbine engine, the exhaust liner and the retractable exhaust liner segment. 
     
     
       21. The retractable exhaust liner segment as recited in  claim 5 , wherein said T-bolt is pivotable through said slot.